EP3400169B1 - Blattverstellung sperren und segelstellung für turbofan blätter - Google Patents

Blattverstellung sperren und segelstellung für turbofan blätter Download PDF

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Publication number
EP3400169B1
EP3400169B1 EP17702673.9A EP17702673A EP3400169B1 EP 3400169 B1 EP3400169 B1 EP 3400169B1 EP 17702673 A EP17702673 A EP 17702673A EP 3400169 B1 EP3400169 B1 EP 3400169B1
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EP
European Patent Office
Prior art keywords
actuator
pitch
propeller
ring
blades
Prior art date
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Application number
EP17702673.9A
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English (en)
French (fr)
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EP3400169A1 (de
Inventor
Emmanuel Pierre Dimitri Patsouris
Sébastien Emile Philippe Tajan
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3400169A1 publication Critical patent/EP3400169A1/de
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
    • B64C11/385—Blade pitch-changing mechanisms fluid, e.g. hydraulic comprising feathering, braking or stopping systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/32—Blade pitch-changing mechanisms mechanical
    • B64C11/325—Blade pitch-changing mechanisms mechanical comprising feathering, braking or stopping systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F04D29/36—Blade mountings adjustable
    • F04D29/362—Blade mountings adjustable during rotation
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to the general field of turbomachines equipped with one or two fan (s) ducted (s) or not careened (s), and more particularly to the control of the orientation of the fan blades (s) of these turbomachinery.
  • a preferred field of application of the invention relates to jet engines with counter-rotating propellers, called "Open Rotors" in English, which comprise two counter-rotating propellers placed downstream (“pusher” version in English) or upstream (“puller” version in English). English) of the gas generator.
  • the invention also applies to turboprop engines with one or more propulsive propellers.
  • the orientation of the blades of the propellers requires taking certain safety measures to ensure that the blades do not remain blocked in certain positions following in particular a malfunction of the control systems of their orientation. For example, under their own centrifugal effect, the blades tend to move into a flat position (or "sail" position which corresponds to a setting for which their rope forms an angle of 90 ° with the axis of rotation of the propeller). However, a blade locked in this flat position generates little resistive torque and may overspeed, with the risk that it involves losing the blade and / or the rotating hub that carries it. A blade stuck in this position may also generate excessive and unacceptable drag for the aircraft.
  • the main object of the present invention is therefore to propose a device for locking the pitch and for feathering the blades of fan with adjustable orientation of a turbomachine propeller (with faired or non-streamlined fan) which does not have the abovementioned disadvantages.
  • the moving part may be a ring gear centered on the axis of rotation of the helix
  • the first mechanical means may be configured to cooperate with the jack in the position of unlocking the pitch of the fan blade to allow the moving part of the cylinder to slide in an extended cylinder stroke
  • the second mechanical means can be angularly offset relative to the first mechanical means and configured to cooperate with the cylinder in the pitch lock position of the fan blade to allow the sliding cylinder movable portion having a reduced cylinder stroke relative to the extended cylinder stroke
  • the actuator may include means for rotating the ring about the axis of rotation of the helix.
  • fan blades is meant here as well the blades of a propeller (in the case of a turbomachine fan without ducted) that the vanes of a blower (in the case of a fan-cooled turbomachine).
  • the device according to the invention makes it possible to limit the angular pitch ranges of the blades of the helix according to the flight phase.
  • This purely mechanical device is reliable, irreversible (the blades can not control the device), easy to implement and provides a significant gain in weight compared to devices using counterweights.
  • this device uses a power source to power the means to rotate the ring around the axis of rotation of the helix which is independent of the energy source used for the control system of the orientation blades, which brings additional reliability gains.
  • Such a device is also perfectly suited to control systems requiring a small radial size.
  • the movable portion of the jack may comprise a flat part and the first mechanical means of the moving part comprise a notch formed at a portion facing the movable part of the jack, such as the inner periphery of the ring when the moving part is a ring, and along which the flat part of the movable part of the jack can slide in the unlocked position of the pitch of the fan blade.
  • the second mechanical means of the movable part may comprise an abutment against which the flat part of the movable cylinder portion abuts in the locking position of the pitch of the fan blade.
  • the device acts as a sequential mechanism in which a movement of the moving part can be effected only according to the position of the movable part of the jack and a movement of the movable portion of the jack can not be effected. perform only according to the position of the moving part.
  • the movable part further comprises third separate mechanical means, that is to say in the case of a ring offset angularly, first and second mechanical means and adapted to cooperate with the jack to bring it into position. position of feathering of the fan blade (especially in the event of failure of the control of their orientation).
  • the third mechanical moving part means may comprise a ramp protruding from a lateral face of said moving part and forming a cam path along which the flat part of the movable part is slid to bring the moving part of the jack into position. feathering of the fan blade.
  • the device is thus irreversible in the sense that the orientation of the ramp can control the orientation of the blades (for their feathering) but the orientation of the blades can not control the orientation of the ramp which has an angle of too much friction with the moving parts of cylinder.
  • the moving part of the device acts as a lock: the moving part of the jack can be moved or not depending on the position of the moving part, that is to say according to the angular position of the crown in the case where the moving part is a crown. Conversely, the moving part can be moved or not depending on the position of the movable part of the jack.
  • the means for rotating the ring around the axis of rotation of the helix may comprise an actuator provided with a pinion gear meshing with teeth carried by the ring gear.
  • the teeth of the ring may be positioned at an outer periphery of the ring and extend angularly over a portion of said ring.
  • the moving part of the jack can be positioned inside the ring.
  • the length of the extended jack stroke preferably corresponds substantially to the stroke allowed during jack flight.
  • the device may comprise three moving parts of jack regularly distributed around the axis of rotation of the propeller.
  • the subject of the invention is also a system for controlling the orientation of the fan blades of a turbomachine, comprising at least one propeller provided with adjustable-orientation fan blades, said propeller being rotatably connected to a rotary ring, the fan blades being coupled, for the adjustment of their orientation, to a jack and a motion transfer bearing system, the system further comprising a device as defined previously for pitch locking and feathering of the blades .
  • the invention further relates to a turbomachine comprising at least one set of adjustable-orientation fan blades and such a system for controlling the orientation of said fan blades.
  • the invention applies to any turbomachine equipped with at least one ducted or non-ducted fan, and whose propeller blades (in the case of a non-ducted fan) or the fan blades (in the case of a fan). a streamlined fan) are equipped with a step change system.
  • the invention applies in particular to turboprop engines with one or more propeller propellers, as well as propeller (s) (known as “Open Rotor”) turbofan engines that comprise a propeller (and a variable-pitch stator for the propeller).
  • propeller s
  • s propeller
  • USF Unducted Single Fan
  • Single non-ducted blower single non-ducted blower
  • two counter-rotating propellers placed upstream (in “puller” version in English) or downstream (in “pusher” version in English) of the gas generator.
  • the invention is still applicable to streamlined fan turbomachines.
  • turbomachines comprise one or more propellers (in the case of a non-ducted fan turbomachine) or a fan (in the case of a fan-cooled turbomachine) each consisting of a set of blades (or blades ) blowers variable pitch angle, that is to say that their orientation can be changed by means of a control system of the orientation of the blades described below.
  • propeller and propeller blades regardless of whether the invention applies to a non-ducted fan turbomachine or to a fan-cooled turbomachine (to which the propeller corresponds to the propeller). blower and propeller blades to fan blades).
  • a turbomachine propeller is constituted by a set of fan blades with variable pitch angle, independent or not, that is to say that their orientation can be modified by means of a control system of the orientation of the blades .
  • this control system may comprise an axial jack 2 centered on the axis of rotation XX of the helix and fixed relative to the engine structures (the axis of rotation of the helix is generally coincident with the axis of the turbomachine but can be shifted in certain configurations).
  • This jack 2 comprises a chamber 4 (ie fixed part) and rods 6 (ie moving parts) which can move axially synchronously when the cylinder is actuated.
  • the rods 6 are connected to the inner ring 8 of a rolling motion transfer bearing 10 whose outer ring 12 is coupled, by means of lever arms 14, to pivots 16 of the blades.
  • fan blower mounted on a rotating ring 17 centered on the axis XX.
  • the rods 6 translate to move the rolling motion transfer bearing 10, resulting in a pivoting of the pivots 16 of the fan blades about their radial axis ZZ and therefore a change of their pitch.
  • the cylinder body is movable (ie moving part) in translation relative to the cylinder rods which are fixed (ie fixed part).
  • a device for locking the pitch of the fan blades, and to flag them in case of failure of the control system of their orientation is provided.
  • FIGS. 2A-2B, 3A-3B and 4A-4B represent a first embodiment of such a device 18 in different operating configurations.
  • the device according to the first embodiment of the invention comprises a ring 20 centered on the axis of rotation X-X of the helix and means for rotating the ring about this axis X-X.
  • the crown is however fixed axially.
  • the ring 20 is intended to cooperate with the rods 6 of the axial jack, here three in number regularly distributed around the axis X-X. More precisely, it is positioned in a plane transverse to the X-X axis of the helix so as to surround the rods 6 of the jack. These are therefore positioned inside the crown.
  • the rods protrude outside the chamber of a length that is at least greater than the stroke. of the cylinder.
  • the stroke of the cylinder makes it possible to bring the controlled blades from a flag position to a most important setting position that they can meet in flight.
  • Each rod 6 comprises a flat portion 6a which is machined in the intermediate portion of the rod which is external to the cylinder chamber.
  • This flat part 6a extends axially over a length that substantially corresponds to the stroke allowed during the flight of the jack.
  • the flats cooperate with notches 20a formed at the inner periphery of the ring 20.
  • the Figures 2A and 2B show (in view of the upstream for the Figure 2A and in view of downstream for the Figure 2B ) the device when it is in such a position of unlocking the pitch of the fan blades, that is to say when it allows the cylinder of the control system of the orientation of the blades to pass a wedging of blades to another.
  • the flat portion 6a of the rods 6 can slide freely along the notches 20a of the ring 20 (along the axis XX) so as to modify the pitch of the blades.
  • the ring 20 of the device according to the invention also comprises abutments 20b which are directly adjacent to the notches 20a and which are each adapted to cooperate with the flat portion 6a of the rods 6 of the jack when the device is in the locking position of the pitch of the blades. blower ( Figures 3A and 3B ).
  • these stops 20b may be in the form of notches forming a stop which prevent the flats 6a of the rods to slide over their entire length.
  • the shoulder of the flats comes into mechanical abutment against these notches.
  • FIGS. 3A and 3B show (in view of the upstream for the figure 3A and in view of downstream for the figure 3B ) the device when the ring 20 is pivoted to be in the locking position of the pitch of the fan blades. In this position, the device limits the stroke of the control cylinder of the orientation of the blades to prevent them from coming into flight in unauthorized stall positions. Unauthorized stall positions include the thrust reversal position and other stalls causing excessive drag.
  • the flat portion 6a of the rods 6 can slide so as to modify the pitch of the blades along the notches 20a of the ring 20 (along the axis XX) but in a limited stroke relative to the unlocking position of the Figures 2A and 2B .
  • the ring 20 of the device according to the invention also comprises ramps 20c forming a cam path which are inserted angularly between the notches 20a and stops 20b and which are adapted to cooperate with the flat portion 6a of the rods 6 of the jack when the device is in position. fan blade feathering position ( Figures 4A and 4B ).
  • These ramps 20c are for example in the form of protuberances projecting from a lateral face of the ring 20 (in the case of Figures 4A and 4B they protrude from the downstream side of the crown).
  • These ramps 20c are in a position which prevents axial displacement of the rods. This position advantageously corresponds to the feathering position of the fan blades (the blades align their rope with the axis of rotation of the propeller).
  • FIGS. 4A and 4B show (in view of the upstream for the Figure 4A and in view of downstream for the Figure 4B ) the device when the crown is rotated angularly to put in position of feathering of the fan blades.
  • the cylinder rods translate axially (the shoulder of their flat abuts against the ramps following the cam path that form these ramps), thus bringing the blades to the position of bet in flag.
  • these means comprise an actuator 22, for example electric, which is provided with a pinion gear 24 meshing with teeth 26 carried by the ring gear 20.
  • the teeth 26 are positioned at an outer periphery of the ring 20 and extend angularly over a portion of said ring.
  • a command makes it possible to control the actuator 22 so as to rotate the ring 20 around the axis XX of rotation of the helix in order to select in which position the device according to the invention must be located (unlocking position of the not blades, blade pitch lock position, and blade feathering position).
  • the ring 20 cooperates with the cylinder rods 6 (via their flat part 6a).
  • the ring cooperates rather with the cylinder body (for example via a flat formed on the body).
  • FIGS. 5A, 5B and 5C represent a second embodiment of such a device 18 in different operating configurations. More specifically, FIGS. 5A to 5C respectively illustrate the device 18 in the unlocking position of the pitch, in the pitch lock position and in the feathering position.
  • the device according to the second embodiment of the invention comprises, for each rod 6 of the jack 2, a cam 200 in translation orthogonal to the rod 6 with which it is associated and means, not shown, to translate the cam 200 orthogonally to the rod 6 between three positions.
  • the rods 6 protrude outside the chamber 4 of a length which is at less than the stroke of the cylinder 2.
  • the stroke of the cylinder 2 makes it possible to bring the blades controlled from a flag position to a most important setting position that they may encounter in flight.
  • each rod 6 comprises a flat part 6a which is machined in the intermediate portion of the rod 6 which is external to the chamber 4 of the jack 2.
  • This flat part 6a extends axially over a length that corresponds substantially at the stroke allowed during the flight of the cylinder 2.
  • the flat portion 6a of a rod 6 cooperates with the notch 200a of the associated cam 200, the notch 200a being formed on a face of the cam 200 next to the rod 6.
  • the Figure 5A shows the device 18 when it is in such a position of unlocking the pitch of the fan blades, that is to say when it allows the cylinder 2 of the control system of the orientation of the blades to pass a wedging the blades to another.
  • this unlocking position when the cylinder 2 is actuated, the flat portion 6a of the rod 6 can slide freely along the notch 200a of the ring 200 (along the axis XX) so as to modify the no blades.
  • Each cam 200 of the device 18 according to the second embodiment of the invention also comprises a stop 200b which is directly adjacent to the notch 200a and which is adapted to cooperate with the flat portion 6a of the rod 6 of the jack 2 to which it is associated when the device 18 is in the position of locking the pitch of the fan blades as shown in FIG. Figure 5B .
  • the notch 200a may be formed by an extrusion in the cam and the abutment 200b may be formed by the cam and more precisely by the thickness of the cam forming a stop which prevents the flat portion 6a of the rod 6 to slide along its entire length.
  • the shoulder of the flat comes into mechanical abutment against the stop 6a.
  • the Figure 5B shows the device 18 when the cam 200 is translated into the locking position of the pitch of the fan blades. In this position, the device 18 limits the stroke of the cylinder 2 of the control system of the orientation of the blades to prevent the latter from coming into flight in unauthorized stall positions. Unauthorized stall positions include the thrust reversal position and other stalls causing excessive drag.
  • the flat portion 6a of the rods 6 can slide so as to modify the pitch of the blades along the notches 200a of the cams 200 but in a limited stroke relative to each other. at the unlock position of the Figure 5A .
  • Each cam 200 of the device 18 according to the second embodiment of the invention also comprises a ramp 200c forming a cam path.
  • the stop 200b of a cam 200 is interposed between the ramp 200c and the notch 200a.
  • the ramp 200c is for example in the form of a protrusion protruding from a side face of the cam 200, that is to say in a direction parallel to the direction in which the rod 6 extends to which the cam 200 is associated.
  • the flat portion 6a of a rod 6 of the jack 2 is slid along the ramp 200c, it is in a position which prevents axial displacement of the rod 6.
  • This position advantageously corresponds to the feathering position of the blades blower (the blades align their rope with the axis of rotation of the propeller).
  • the Figure 5C thus shows the device 18 when the cam 200 is translated to put in the position of feathering of the fan blades.
  • the rods 6 of the cylinder 2 translate axially (the shoulder of their flat 6a abuts against the ramps 6c along the cam path formed by these ramps 6c), thus reducing the blades up to 'at the feathering position.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (13)

  1. Vorrichtung (18) zum Verriegeln der Steigung und zum Verstellen in Richtung Fahne von Gebläseschaufeln mit einstellbarer Ausrichtung eines Turbomaschinenpropellers, umfassend:
    einen Zylinder (2), der wenigstens einen beweglichen Teil (6) umfasst, welcher sich parallel zu einer Drehachse (X-X) des Propellers erstreckt und welcher dazu bestimmt ist, mit Drehzapfen (16) der Gebläseschaufeln des Propellers gekoppelt zu werden, um deren Steigungseinstellung zu verändern, wenn er sich verschiebt, dadurch gekennzeichnet, dass die Vorrichtung umfasst
    ein gegenüber dem Zylinder (2) bewegliches Teil (20, 200) mit ersten mechanischen Mitteln (20a, 200a), die geeignet sind, in der Stellung des Entriegelns der Steigung der Gebläseschaufel mit dem Zylinder (2) zusammenzuwirken, um dem beweglichen Zylinderteil (6) zu ermöglichen, sich entlang eines großen Zylinderhubs zu verschieben, sowie zweiten mechanischen Mitteln (20b, 200b), die von den ersten mechanischen Mitteln (20a, 200a) verschieden und geeignet sind, in der Stellung des Verriegelns der Steigung der Gebläseschaufel mit dem Zylinder (2) zusammenzuwirken, um dem beweglichen Zylinderteil (6) zu ermöglichen, sich entlang eines gegenüber dem großen Zylinderhub verkürzten Zylinderhubs zu verschieben, und
    einen Aktor (22, 24, 26), um das bewegliche Teil (20, 200) zwischen der Entriegelungsstellung des Zylinders (2) und der Verriegelungsstellung des Zylinders (2) zu bewegen.
  2. Vorrichtung nach Anspruch 1, bei der der bewegliche Zylinderteil eine Abflachung (6a) aufweist und die ersten mechanischen Mittel des beweglichen Teils eine Nut (20a, 200a) umfassen, die im Bereich eines Teils gegenüber dem beweglichen Teil des Zylinders ausgebildet ist und entlang derer die Abflachung des beweglichen Zylinderteils in der Stellung des Entriegelns der Steigung der Gebläseschaufel gleiten kann.
  3. Vorrichtung nach Anspruch 1, bei der der bewegliche Zylinderteil eine Abflachung (6a) aufweist und die zweiten mechanischen Mittel des beweglichen Teils einen Anschlag (20b, 200b) umfassen, an dem die Abflachung des beweglichen Zylinderteils in der Stellung des Verriegelns der Steigung der Gebläseschaufel in Anschlag gelangt.
  4. Vorrichtung nach Anspruch 1, bei der das bewegliche Teil (20, 200) ferner dritte mechanische Mittel (20c, 200c) umfasst, die von den ersten und zweiten mechanischen Mitteln verschieden und geeignet sind, mit dem Zylinder zusammenzuwirken, um ihn in die Position zur Verstellung der Gebläseschaufel in Richtung Fahne zu bringen.
  5. Vorrichtung nach Anspruch 4, bei der der bewegliche Zylinderteil eine Abflachung (6a) aufweist und die dritten mechanischen Mittel des beweglichen Teils eine Rampe (20c) umfassen, die von einer Seitenfläche des beweglichen Teils vorspringt und einen Nockenweg bildet, entlang dessen die Abflachung des beweglichen Zylinderteils gleitet, um den beweglichen Zylinderteil in die Position zur Verstellung der Gebläseschaufel in Richtung Fahne zu bringen.
  6. Vorrichtung nach Anspruch 1, bei der der bewegliche Teil einen Kranz (20) umfasst, der um die Drehachse des Propellers zentriert ist, wobei die ersten mechanischen Mittel (20a) dazu ausgelegt sind, in der Stellung des Entriegelns der Steigung der Gebläseschaufel mit dem Zylinder zusammenzuwirken, um dem beweglichen Zylinderteil zu ermöglichen, sich entlang eines großen Zylinderhubs zu verschieben, die zweiten mechanischen Mittel (20b) gegenüber den ersten mechanischen Mitteln winkelmäßig versetzt und dazu ausgelegt sind, in der Stellung des Verriegelns der Steigung der Gebläseschaufel mit dem Zylinder zusammenzuwirken, um dem beweglichen Zylinderteil zu ermöglichen, sich entlang eines gegenüber dem großen Zylinderhub verkürzten Zylinderhubs zu verschieben, und der Aktor Mittel (22, 24, 26) umfasst, um den Kranz um die Drehachse des Propellers zu drehen.
  7. Vorrichtung nach Anspruch 6, bei der die Mittel zum Drehen des Kranzes (20) um die Drehachse des Propellers einen Aktor (22) umfassen, der mit einem Zahnritzel (24) versehen ist, das mit von dem Kranz getragenen Zähnen (26) kämmt.
  8. Vorrichtung nach Anspruch 7, bei der die Zähne des Kranzes im Bereich eines Außenumfangs des Kranzes angeordnet sind und sich über einen Abschnitt des Kranzes winkelig erstrecken.
  9. Vorrichtung nach einem der Ansprüche 6 bis 8, bei der der bewegliche Zylinderteil (6) innerhalb des Kranzes (20) angeordnet ist.
  10. Vorrichtung nach einem der Ansprüche 1 bis 9, bei der der große Zylinderhub im Wesentlichen dem während des Fluges zulässigen Hub des Zylinders entspricht.
  11. Vorrichtung nach einem der Ansprüche 1 bis 10, umfassend wenigstens drei bewegliche Zylinderteile, die um die Drehachse des Propellers gleichmäßig verteilt sind.
  12. System zum Steuern der Ausrichtung der Gebläseschaufeln einer Turbomaschine, umfassend wenigstens einen Propeller, der mit Gebläseschaufeln mit einstellbarer Ausrichtung versehen ist, wobei der Propeller mit einem Drehring (17) drehfest verbunden ist, wobei die Gebläseschaufeln für die Einstellung ihrer Ausrichtung mit einem System mit Zylinder (6) und Bewegungsübertragungslager (10) gekoppelt sind, wobei das System ferner eine Vorrichtung (18) nach einem der Ansprüche 1 bis 11 umfasst.
  13. Turbomaschine, umfassend wenigstens eine Anordnung von Gebläseschaufeln mit einstellbarer Ausrichtung und ein System zum Steuern der Ausrichtung der Gebläseschaufeln nach Anspruch 12.
EP17702673.9A 2016-01-05 2017-01-04 Blattverstellung sperren und segelstellung für turbofan blätter Active EP3400169B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1650041A FR3046408B1 (fr) 2016-01-05 2016-01-05 Dispositif pour le verrouillage du pas et la mise en drapeau de pales de soufflante a orientation reglable d'une helice de turbomachine
PCT/FR2017/050012 WO2017118809A1 (fr) 2016-01-05 2017-01-04 Dispositif pour le verrouillage du pas et la mise en drapeau de pales de soufflante à orientation réglable d'une hélice de turbomachine

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EP3400169A1 EP3400169A1 (de) 2018-11-14
EP3400169B1 true EP3400169B1 (de) 2019-11-13

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US (1) US10689094B2 (de)
EP (1) EP3400169B1 (de)
CN (1) CN108602552B (de)
FR (1) FR3046408B1 (de)
WO (1) WO2017118809A1 (de)

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CN110040240B (zh) * 2019-05-24 2023-09-22 安阳市豪克航空科技有限公司 单驱动螺旋桨变距、顺桨、停桨位锁定系统
FR3104540B1 (fr) * 2019-12-11 2021-12-17 Safran Aircraft Engines Perfectionnement au verrouillage radial d’un pivot d’aube à orientation réglable pour moyeu de soufflante de turbomachine
CN111058903B (zh) * 2020-02-18 2020-09-29 潍坊联信增压器股份有限公司 一种具有保护功能的涡轮发动机
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Publication number Publication date
CN108602552A (zh) 2018-09-28
FR3046408B1 (fr) 2018-02-09
US20190009886A1 (en) 2019-01-10
WO2017118809A1 (fr) 2017-07-13
US10689094B2 (en) 2020-06-23
EP3400169A1 (de) 2018-11-14
FR3046408A1 (fr) 2017-07-07
CN108602552B (zh) 2022-06-17

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